An aircraft control system includes a co-axial, counter-rotating propeller shaft assembly (28 fig. 1) that comprises a first rotor 34 operatively coupled to the propeller shaft assembly, the first rotor having a first plurality of blades 38 mounted thereto, wherein the first plurality of blades are disposed at a substantially identical nominal pitch during rotation of the first rotor. Further included is a second rotor 40 operatively coupled to the propeller shaft assembly, the second rotor having a second plurality of blades 44 mounted thereto, wherein a pitch of the second plurality of blades is configured to cyclically change during rotation of the second rotor. The second rotor may be disposed upstream or downstream of the first rotor and may be proximate a fixed wing (82 fig.3) or a nose of an aircraft. The pitch of the second plurality of blades may be altered cyclically to generate a moment configured to control the aircraft.


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    Titel :

    Aircraft control system and method


    Beteiligte:
    HENZE CHAD M (Autor:in) / PERKINSON ROBERT H (Autor:in)

    Erscheinungsdatum :

    2015-07-15


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    B64C AEROPLANES , Flugzeuge



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